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Swept-Wing Icing Research
Swept-Wing Icing and Aerodynamics Research
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 Portion of the Common Research Model wing installed in the Icing Research Tunnel at NASA Glenn Research Center. |
Goal of Project
Improve the fidelity of experimental and computational simulation methods for swept-wing ice accretion formation and resulting aerodynamic effect.
Objectives
- Generate a database of 3D ice-accretion geometry for icing code development and validation; and for aerodynamic testing..
- Develop a systematic understanding of the aerodynamic effect of icing on swept-wings including: Reynolds and Mach number effects, important flowfield physics and fundamental differences from 2D..
- Determine the level of geometric fidelity required for accurate aerodynamic simulation of swept-wing icing effects.
